To address the inadequacies of supersonic combustion, this study employed the DMD method to extract features from supersonic combustion flows utilizing pulsed fuel injection, and based on these findings, implemented NS-SDBD for flow control. The FVM was employed to solve the multi-component 2D URANS equations with the SST k-ω turbulence model. The combustion flow of a transverse pulsed H2 jet at an incoming Mach number of 2.5 was simulated, and the characteristics of the temperature field were extracted. The flow can be effectively reconstructed by using all modes, resulting in an average error of only 2.8%. The method for determining the actuator frequency based on the results obtained from DMD method is feasible. After applying 20 kHz actuation, the average mass fraction of H2O increased by 5.1% and this effect increased with the progression of the flow. The coupling effects of the pulsed jet and NS-SDBD drove high-temperature air into the dense hydrogen interior.